U.S. patent application number 15/410129 was filed with the patent office on 2017-10-26 for piezoelectric damping rings.
The applicant listed for this patent is Rolls-Royce Corporation. Invention is credited to Roy D. Fulayter, Daniel Hoyniak.
Application Number | 20170306772 15/410129 |
Document ID | / |
Family ID | 60090022 |
Filed Date | 2017-10-26 |
United States Patent
Application |
20170306772 |
Kind Code |
A1 |
Fulayter; Roy D. ; et
al. |
October 26, 2017 |
PIEZOELECTRIC DAMPING RINGS
Abstract
A blisk assembly for vibration dampening includes a disk portion
extending circumferentially about a central axis of the blisk, a
plurality of blades integrally coupled to the disk, and a
piezoelectric damping ring that includes a damping ring and a
plurality of piezoelectric elements coupled to the damping ring.
The disk portion includes a groove configured to receive the
piezoelectric damping ring. As a result of centrifugal forces
applied to the piezoelectric damping ring during rotation of the
blisk assembly, mechanical energy may be generated at one or more
of the plurality of piezoelectric elements, which is converted to
electrical energy and transmitted to another one or more of the
plurality of piezoelectric elements. Accordingly, the one or more
of the piezoelectric elements having received the electricity can
convert the electricity to mechanical energy to provide vibration
damping.
Inventors: |
Fulayter; Roy D.; (Avon,
IN) ; Hoyniak; Daniel; (Carmel, IN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
Rolls-Royce Corporation |
Indianapois |
IN |
US |
|
|
Family ID: |
60090022 |
Appl. No.: |
15/410129 |
Filed: |
January 19, 2017 |
Related U.S. Patent Documents
|
|
|
|
|
|
Application
Number |
Filing Date |
Patent Number |
|
|
14845478 |
Sep 4, 2015 |
|
|
|
15410129 |
|
|
|
|
62048071 |
Sep 9, 2014 |
|
|
|
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
F04D 29/668 20130101;
Y02T 50/672 20130101; F01D 25/04 20130101; F05D 2260/407 20130101;
F01D 5/12 20130101; F04D 29/321 20130101; F05D 2220/32 20130101;
F05D 2260/96 20130101; Y02T 50/60 20130101; F04D 29/324 20130101;
F05D 2260/962 20130101; F01D 5/10 20130101; F01D 5/34 20130101 |
International
Class: |
F01D 5/34 20060101
F01D005/34; F01D 25/04 20060101 F01D025/04; F01D 5/10 20060101
F01D005/10; F04D 29/66 20060101 F04D029/66 |
Claims
1. A blisk assembly adapted for use in a gas turbine engine, the
blisk assembly comprising a disk extending circumferentially about
a central axis of the blisk assembly, a plurality of blades
integrally coupled to the disk that extend outwardly from the disk
in a radial direction away from the central axis, and a
piezoelectric damping ring that includes a damping ring and a
plurality of piezoelectric elements coupled to the damping ring,
wherein the piezoelectric damping ring forms a full hoop around the
central axis and each of the piezoelectric elements is configured
to convert electrical energy in response to generation of
mechanical energy and to convert received electrical energy to
mechanical energy in response to receipt of the electrical energy
from another of the piezoelectric elements so that vibrations of
the blisk assembly are dampened by distribution of energy across
one or more of the piezoelectric elements.
2. The blisk assembly of claim 1, further comprising a plurality of
wires, wherein each wire connects at least two of the plurality of
piezoelectric elements to each other to transmit electricity
therebetween.
3. The blisk assembly of claim 1, wherein the damping ring is
coupled to the disk by a plurality of fasteners at a first radius
and the damping ring contacts another portion of the blisk assembly
at a second radius spaced apart from the plurality of fasters to
allow for relative movement of the damping ring relative to the
disk at the second radius.
4. The blisk assembly of claim 3, wherein the second radius is
located outward of the first radius.
5. The blisk assembly of claim 4, wherein the plurality of
piezoelectric elements arranged at a third radius spaced apart from
the first radius to allow for relative movement of the
piezoelectric elements relative to the disk.
6. The blisk assembly of claim 5, wherein the third radius is
located between the first radius and the second radius.
7. The blisk assembly of claim 1, wherein each of the piezoelectric
elements are coupled to the damping ring using discrete
bonding.
8. The blisk assembly of claim 1, wherein each of the piezoelectric
elements includes a metal spray coating to provide an electrically
conductive means to send and receive power.
9. The blisk assembly of claim 1, wherein the plurality of
piezoelectric elements comprises a first piezoelectric element and
a second piezoelectric element, wherein each of the first and
second piezoelectric elements are connected via a wire, wherein the
first piezoelectric element is configured to transmit electricity
converted from mechanical energy received at the first
piezoelectric element to the second piezoelectric element.
10. The blisk assembly of claim 9, wherein the first and second
piezoelectric elements are coupled to the damping ring in different
locations along the damping ring to send and received vibration
from different nodal diameter patterns.
11. The blisk assembly of claim 9, wherein each of the
piezoelectric elements are circumferentially spaced an equidistant
amount from neighboring piezoelectric elements.
12. The blisk assembly of claim 1, further comprising a platform
integrally formed with the disk and the plurality of blades that
separates the disk from the plurality of blades so that gasses
passing over the blades does not interact with the disk, and
wherein the damping ring is coupled to the disk by a plurality of
fasteners at a first radius and the damping ring contacts the
platform at a second radius radially outward of the plurality of
fasters to allow for relative movement of the damping ring relative
to the disk at the second radius.
13. The blisk assembly of claim 12, wherein the disk is formed to
include a cantilevered flange to which the damping ring is
fastened.
14. The blisk assembly of claim 12, wherein the damping ring
contacts the platform near a mid-span of the plurality of
blades.
15. The blisk assembly of claim 12, wherein the damping ring
contacts the platform at an aft end of the platform.
16. The blisk assembly of claim 12, wherein the damping ring
contacts the platform at forward end of the platform.
17. A method of vibration damping of a blisk adapted for use in a
gas turbine engine, the method comprising providing a piezoelectric
damping ring to a disk included in the blisk, wherein the
piezoelectric damping ring comprises a damping ring and a plurality
of piezoelectric elements coupled to the damping ring, the damping
ring fastened to the disk at a first location and contacting
another portion of the blisk spaced apart from the first location
to allow microslip between the damping ring and the rest of the
blisk; rotating the blisk to generate centrifugal force on the
piezoelectric damping ring and to generate micro-sleep between the
piezoelectric damping ring and the disk; transferring electricity
from a first piezoelectric element of the plurality of
piezoelectric elements to a second piezoelectric element of the
plurality of piezoelectric elements; dampening vibrations of the
blisk as a function of the electricity received at the second
piezoelectric element.
18. The method of claim 17, wherein transferring the electricity
from the first piezoelectric element to the second piezoelectric
element comprises: capturing mechanical energy at the first
piezoelectric element as a product of micro-slip between the
piezoelectric damping ring and the disk; converting the mechanical
energy to electricity at the first piezoelectric element;
transmitting, via a wire coupling the first piezoelectric element
to the second piezoelectric element, the electricity from the first
piezoelectric element to the second piezoelectric element; and
converting the electricity to mechanical energy at the second
piezoelectric element.
19. The method of claim 18, wherein dissipating the mechanical
energy at the second piezoelectric element comprises dissipating
the mechanical energy as a product of mechanical friction between
the piezoelectric damping ring and the disk.
20. The method of claim 19, further comprising dissipating the
mechanical energy through heat due to mechanical friction at the
second piezoelectric element.
Description
CROSS-REFERENCE TO RELATED U.S. APPLICATION
[0001] This application is a continuation-in-part of U.S. patent
application Ser. No. 14/845,478 filed 4 Sep. 2015, which claims
priority to and the benefit of U.S. Provisional Patent Application
62/048,071, filed 9 Sep. 2014, the original disclosures of both
cross-referenced applications are now expressly incorporated herein
by reference.
FIELD OF THE DISCLOSURE
[0002] The present disclosure relates generally to turbofan
engines, including but not limited to those used in propulsion
drive systems, such as aircrafts. More specifically, the present
disclosure relates to using piezoelectric damping rings for use in
turbomachinery blisks (i.e., bladed disks) for dampening
vibrations.
BACKGROUND
[0003] Gas turbine engines can be used as a primary power source to
power aircraft, watercraft, and other types of vehicles, as well as
power generators and the like. For example, aerospace applications
of gas turbine engines include turboshaft, turboprop, and turbofan
engines. Gas turbine engines typically include one or more
compressors, a combustor, and one or more turbines. In typical
aerospace applications, a fan or propeller is used to provide the
majority of the engine thrust and is located in front of the core
engine. The compressor, in which inlet air is compressed, includes
alternating stages of rotating blades and static vanes, which
increase the pressure of the air as it travels through the gas
turbine core.
[0004] The compressor outputs higher-pressure air, which it
delivers to the combustor, wherein fuel is combusted with the
compressed air. As a result, exhaust gas is generated and directed
to the one or more turbines, wherein the exhaust gas can be used to
rotate one or more rotating disks with blades integrally attached.
In typical aerospace applications, the gas turbine engine provides
thrust to propel the aircraft, and also supplies power for
accessories of the engine and/or the aircraft. Accordingly, such
integrally bladed rotors, or blisks (i.e., bladed disks), can
additionally and/or alternatively be used for other components of
the gas turbine engines, such as compressors, fan blade rotors,
etc.
[0005] Each blisk consists of a single element combining both a
rotor disk and blades, as opposed to a disk and a plurality of
individual, removable blades. Typically, during operation of
turbofan engines, vibration, such as harmonic vibration from the
blades of the blisk, is introduced. Such vibration may introduce
engine wear, thereby reducing engine life. Accordingly, such blisks
are generally required to undergo harmonic vibration testing.
Conventional technologies to mitigate the vibrations include
damping rings, which may be used on blisks of turbofan engines, to
reduce or otherwise dampen such vibration when relative motion
exists on the disk rim and the damping ring, for example.
SUMMARY
[0006] The present disclosure may comprise one or more of the
following features and combinations thereof.
[0007] According to one aspect of the present disclosure, a blisk
assembly adapted for use in a gas turbine engine includes a disk
extending circumferentially about a central axis of the blisk
assembly, wherein the disk includes a groove that extends
circumferentially about a portion of the disk axisymmetric about
the central axis, and wherein the groove is substantially concave
in shape. The blisk assembly additionally includes a plurality of
blades integrally coupled to the disk that extend outwardly from
the disk in a radial direction away from the central axis. The
blisk assembly further includes a piezoelectric damping ring that
includes a damping ring and a plurality of piezoelectric elements
coupled to the damping ring. The piezoelectric damping ring extends
substantially around the central axis within the groove and each of
the piezoelectric elements is configured to convert electrical
energy in response to generation of mechanical energy and to
convert received electrical energy to mechanical energy in response
to receipt of electrical energy from another of the piezoelectric
elements so that vibrations of the blisk assembly are dampened by
distribution of energy across one or more of the piezoelectric
elements.
[0008] In some embodiments, the blisk assembly may further include
a plurality of wires, wherein each wire connects at least two of
the plurality of piezoelectric elements to each other to transmit
the electricity therebetween.
[0009] In some embodiments, the blisk assembly may further include
another piezoelectric damping ring that is located in another
groove that extends circumferentially about another portion of the
disk axisymmetric around the central axis.
[0010] In some embodiments, each of the piezoelectric elements are
coupled to the damping ring using discrete bonding.
[0011] In some embodiments, each of the piezoelectric elements
includes a metal spray coating to provide an electrically
conductive means to send and receive power.
[0012] In some embodiments, each of the piezoelectric elements are
comprised of ceramic composite material.
[0013] In some embodiments, the plurality of piezoelectric elements
comprises a first and second piezoelectric element, wherein each of
the first and second piezoelectric elements are connected via a
wire, wherein the first piezoelectric element is configured to
transmit electricity converted from mechanical energy received at
the first piezoelectric element to the second piezoelectric
element.
[0014] In some embodiments, the first and second piezoelectric
elements are coupled to the damping ring in different locations
along the damping ring to send and received vibration from
different nodal diameter patterns.
[0015] In some embodiments, each of the piezoelectric elements are
circumferentially spaced an equidistant amount from neighboring
piezoelectric elements.
[0016] In some embodiments, each of the piezoelectric elements is
connected to another of the piezoelectric elements via a wire.
[0017] In some embodiments, every other of the piezoelectric
elements is connected to another of the piezoelectric elements via
a wire.
[0018] In some embodiments, the groove defines a radially inwardly
opening channel.
[0019] According to yet another aspect of the present disclosure, a
piezoelectric damping ring assembly adapted for use in a blisk of a
gas turbine engine, the piezoelectric damping ring includes a
damping ring that extends circumferentially about a central axis
and a plurality of piezoelectric elements coupled to a surface of
the damping ring that faces the central axis, wherein each of the
piezoelectric elements are equally spaced about the damping ring,
and wherein each of the piezoelectric elements are configured to
(i) receive mechanical energy, (ii) convert the stored mechanical
energy to electricity, (iii) transmit the electricity to another of
the piezoelectric elements, (iv) receive converted electricity from
another of the piezoelectric elements, and (v) convert the received
converted electricity to mechanical energy to dampen vibrations of
the blisk.
[0020] In some embodiments, the piezoelectric damping ring assembly
includes a plurality of wires, wherein each wire connects at least
two of the plurality of piezoelectric elements to each other to
transmit electricity therebetween.
[0021] In some embodiments, each of the piezoelectric elements are
coupled to the damping ring using discrete bonding.
[0022] In some embodiments, each of the piezoelectric elements are
comprised of ceramic composite material and wherein each of the
piezoelectric elements includes a metal spray coating to provide an
electrically conductive means to send and receive power.
[0023] According to still another aspect of the present disclosure,
a method of vibration damping of a blisk adapted for use in a gas
turbine engine includes providing a piezoelectric damping ring in a
groove extending outward in a radial direction from a radially
inward facing surface of a disk portion of the blisk, wherein the
groove extends circumferentially about a portion of the disk
axisymmetric around a central axis of the blisk, and wherein the
piezoelectric damping ring comprises a damping ring and a plurality
of piezoelectric elements coupled to the damping ring, rotating the
blisk to generate centrifugal force on the piezoelectric damping
ring to generate micro-sleep between the piezoelectric damping ring
and the disk, transferring electricity from a first piezoelectric
element of the plurality of piezoelectric elements to a second
piezoelectric element of the plurality of piezoelectric elements,
and dampening vibrations of the blisk as a function of the
electricity received at the second piezoelectric element.
[0024] In some embodiments, transferring the electricity from the
first piezoelectric element to the second piezoelectric element
includes capturing mechanical energy at the first piezoelectric
element as a product of the micro-slip between the piezoelectric
damping ring and the disk, converting the mechanical energy to
electricity at the first piezoelectric element, transmitting, via a
wire coupling the first piezoelectric element to the second
piezoelectric element, the electricity from the first piezoelectric
element to the second piezoelectric element, and converting the
electricity to mechanical energy at the second piezoelectric
element.
[0025] In some embodiments, dissipating the mechanical energy at
the second piezoelectric element comprises dissipating the
mechanical energy as a product of mechanical friction between the
piezoelectric damping ring and the disk.
[0026] In some embodiments, the method further includes dissipating
the mechanical energy through heat due to mechanical friction at
the second piezoelectric element.
[0027] According to another aspect of the present disclosure,
further blisk assemblies adapted for use in gas turbine engine are
described. Blisk assemblies in accordance with these embodiments
may include a disk extending circumferentially about a central axis
of the blisk assembly, a plurality of blades integrally coupled to
the disk that extend outwardly from the disk in a radial direction
away from the central axis, and a piezoelectric damping ring that
includes a damping ring and a plurality of piezoelectric elements
coupled to the damping ring.
[0028] In illustrative embodiments, the piezoelectric damping ring
may form a full hoop around the central axis. Each of the
piezoelectric elements included in the piezoelectric damping ring
may be configured to convert electrical energy in response to
generation of mechanical energy. Each of the piezoelectric elements
included in the piezoelectric damping ring may also be configured
to convert received electrical energy to mechanical energy in
response to receipt of the electrical energy from another of the
piezoelectric elements. Accordingly vibrations of the blisk
assembly may be dampened by distribution of energy across one or
more of the piezoelectric elements.
[0029] These and other features of the present disclosure will
become more apparent from the following description of the
illustrative embodiments.
BRIEF DESCRIPTION OF THE DRAWINGS
[0030] FIG. 1 is a cutaway view of a gas turbine engine including a
compressor upstream of a combustor for providing compressed air to
the combustor and showing that the compressor includes one or more
blisks arranged therein;
[0031] FIG. 2 is a perspective view of one blisk included in the
compressor of FIG. 1 showing a single element assembly comprising a
disk and a plurality of blades integrally oriented about outer
portion of the disk and a groove extending circumferentially about
the underside of the disk;
[0032] FIG. 3 is a perspective view of the blisk of FIG. 2 showing
that the groove includes a piezoelectric damping ring mounted
therein;
[0033] FIG. 4 is a cross-section view of a portion of the disk
showing the groove including the piezoelectric damping ring of FIG.
3;
[0034] FIG. 5 is an illustration of a Campbell diagram that
illustrates the operational behavior during operating modes of the
gas turbine engine of FIG. 1;
[0035] FIG. 6 is a cross-section view of a second blisk assembly
adapted for use in a compressor showing that the second blisk
assembly includes integrated disk, platform, and blades that form a
blisk along with a piezoelectric damping ring for damping
vibrations induced in the blisk during use, and showing that the
piezoelectric damping ring is fastened to a flange formed by the
disk portion and contacts the platform of the blisk near a mid-span
region of the blades;
[0036] FIG. 7 is a rear elevation view of the second blisk assembly
of FIG. 6 showing the piezoelectric damping ring includes a full
hoop damping ring fastened to the blisk and a plurality of
piezoelectric elements coupled to the full hoop damping ring;
[0037] FIG. 8 is a cross-section view of a third blisk assembly
adapted for use in a compressor, similar to that shown in FIGS. 6
and 7, showing that the third blisk assembly includes integrated
disk, platform, and blades that form a blisk along with a
piezoelectric damping ring for damping vibrations induced in the
blisk during use, and showing that the piezoelectric damping ring
is fastened to a bend formed by the disk of the blisk and contacts
the platform of the blisk at an aft end of the platform;
[0038] FIG. 9 is a cross-section view of a fourth blisk assembly
adapted for use in a compressor, similar to that shown in FIGS. 6
and 7, showing that the fourth blisk assembly includes integrated
disk, platform, and blades that form a blisk along with a
piezoelectric damping ring for damping vibrations induced in the
blisk during use, and showing that the piezoelectric damping ring
is fastened to a flange formed by the disk of the blisk and
contacts the platform of the blisk at an aft end;
[0039] FIG. 10 is a cross-section view of a fifth blisk assembly
adapted for use in a compressor, similar to that shown in FIGS. 6
and 7, showing that the fifth blisk assembly includes integrated
disk, platform, and blades that form a blisk along with a
piezoelectric damping ring for damping vibrations induced in the
blisk during use, and showing that the piezoelectric damping ring
is fastened to a flange formed by the disk of the blisk and
contacts the platform portion at a forward end; and
[0040] FIG. 11 is a cross-section view of a sixth blisk assembly
adapted for use in a compressor, similar to that shown in FIGS. 6
and 7, showing that the sixth blisk assembly includes integrated
disk, platform, and blades that form a blisk along with a
piezoelectric damping ring for damping vibrations induced in the
blisk during use, and showing that the piezoelectric damping ring
is fastened to a drive arm of the disk and contacts the platform
portion at a forward end.
DETAILED DESCRIPTION OF THE DRAWINGS
[0041] For the purposes of promoting an understanding of the
principles of the disclosure, reference will now be made to a
number of illustrative embodiments illustrated in the drawings and
specific language will be used to describe the same.
[0042] An illustrative gas turbine engine 100 for use in aircraft
includes an air intake 102, a compressor 104, a combustor 106, and
a turbine 108. The compressor 104 may be used to compress air drawn
into the air intake 102 of the gas turbine engine 100 by a fan 110,
which delivers at least a portion of intake air into the compressor
104. The compressor 104 may be comprised of one or more compressors
configured to provide the compressed air (i.e., high pressure air)
to the combustor 106. The illustrative compressor includes an
intermediate pressure compressor 116 and a high pressure compressor
118.
[0043] In the combustor 106, fuel is mixed with the high pressure
air and is ignited, the products (e.g., exhaust gases) of which are
directed into the turbine 108 where energy is extracted to drive
the compressor 104 and, typically, one or more shafts of the
turbine 108 (e.g., for powering the fan 110). In some embodiments,
the turbine 108 may include a low power turbine, an intermediate
power turbine, and/or a high power turbine, each of which may be
single or multi-stage turbines. In other embodiments, such as in
steam turbine applications, for example, the turbine 108 may
additionally or alternatively include a low pressure turbine, an
intermediate pressure turbine, and/or a high pressure turbine, each
of which may be single or multi-stage turbines.
[0044] In the illustrative gas turbine engine 100, one or more
blisks 112, or bladed disks, also commonly referred to as
integrally bladed rotors (IBRs), are illustratively shown in the
compressor 104 of the gas turbine engine 100 extending around a
central axis 114 of the gas turbine engine 100. It should be
appreciated that, in some embodiments, the blisks 112 may be
located in additional and/or alternative locations, such as the fan
110, the turbine 108, or any other rotating component of the gas
turbine engine 100.
[0045] As shown in FIG. 2, the illustrative blisk 112 includes a
plurality of blades 204 integrally coupled circumferentially about
an outer side of a rotor disk 202 that is capable of being coupled
to a shaft of a rotor assembly of a rotary mechanical device (e.g.,
a power turbine shaft (not shown) of the gas turbine engine 100).
The blisk may be comprised of a single, solid piece of material
that includes a disk portion and a plurality of blades extending
therefrom, thereby eliminating the use of screws, bolts, or other
coupling materials typically used to attach blades to a disk.
Accordingly, various manufacturing processes may be used to
manufacture the blisk 112; however, such processes are beyond the
scope of the present application. For example, in some embodiments,
one or more of the blades may be welded onto the disk portion of
the blisks 112.
[0046] The illustrative blisk 112 additionally includes a groove
206 on the underside of the disk 202. In some embodiments, the
groove 206 may be located on a thin portion extending outwardly
from the disk 202 (e.g., a lip extending from the disk 202). The
groove 206 has a generally concave shape that extends
circumferentially about the central axis 114 on the underside of
the disk 202. The groove 206 includes an opening 208 and a surface
210, or recessed portion. As shown in FIG. 3, the groove 206 is
configured to receive a piezoelectric damping ring 300 coupled to,
or otherwise in relative contact to, the surface 210 of the groove
206. It should be appreciated that, in some embodiments, rotational
loads may hold the piezoelectric damping ring 300 in place within
the groove 206.
[0047] Referring now to FIG. 3, the groove 206 is shown that
includes an illustrative embodiment of the piezoelectric damping
ring 300 coupled thereto. The illustrative piezoelectric damping
ring 300 includes a damping ring 302 and a plurality of
piezoelectric elements 304 coupled to the damping ring 302. In use,
as described in further detail below, the piezoelectric damping
ring 300 is capable of providing additional damping over
traditional damping rings. For example, the piezoelectric damping
ring 300 may be used to further reduce vibration by transferring
electricity across piezoelectric elements, as described in further
detail below, such as may be generated when relative motion (e.g.,
micro-slip) exists between the disk 202 and the damping ring 302.
Accordingly, the damping ring 302 should be manufactured using a
metal (e.g., brass or other like soft metal) softer than the metal
of the blisk 112, such that the damping ring 302 cannot wear
through the disk 202. In other words, the sacrificial material
should be the damping ring 302 and not the blisk 112.
[0048] The damping ring 302 includes an outward facing portion 308
and in inward facing portion 310, as well as a split 312. As shown,
the outward facing portion 308 is coupled to at least a portion of
the surface 210 of the groove 206. In other words, 360.degree. of
the damping ring 302, with the exception of the split 312, touches
the surface 210 of the groove 206. Accordingly, mechanical damping
may be accomplished by micro-slip generated between the damping
ring 302 and the disk 202, which can result from different spring
constants of the blisk 112 and the damping ring 302 reflecting
differently.
[0049] The piezoelectric damping ring 300 includes a plurality of
piezoelectric elements 304, each of which are coupled to the
damping ring 302 at different circumferential locations about the
inward facing portion 310 of the damping ring 302 at an outward
facing portion 314 of the piezoelectric elements 304. It should be
appreciated that any known technology may be used to couple the
piezoelectric elements 304 to the damping ring 302. For example, in
some embodiments, the piezoelectric elements 304 may be discretely
bonded to the damping ring 302. Additionally or alternatively, in
some embodiments, a thin metal spray coating may be applied to each
of the piezoelectric elements 304 to protect the piezoelectric
elements from adverse conditions (e.g., particulate matter) and
provide an electrically conductive means to send and receive power.
Additionally, each of the piezoelectric elements 304 may be made of
any suitable material capable of performing the functions described
herein, such as ceramic strips bonded to the damping ring 302, for
example. Accordingly, in such an embodiment, the piezoelectric
damping ring 300 may additionally dissipate heat.
[0050] As described previously, if one of the piezoelectric
elements 304 of the piezoelectric damping ring 300 becomes excited
by motion, mechanical energy may be received by that excited
piezoelectric element 304. This may cause the piezoelectric damping
ring 300 to vibrate at another part of the piezoelectric damping
ring 300 due to electrical connections between different
circumferential positions. The piezoelectric damping ring 300 may
then slowly rotate relative to the blisk 112 or slowly rotate
relative to a stationary vane, such as in a snake like motion. This
relative movement may cause additional friction damping, creating
heat, which can be dissipated at least partially, such as by
creating mechanical friction between the piezoelectric damping ring
300 and the groove 206 of the disk 202. To do so, as also described
previously, the mechanical energy received by the excited
piezoelectric element 304 can be converted to electricity, which
can then be transmitted to another of the piezoelectric elements
304 connected to the excited piezoelectric element 304 and
dissipated at the other piezoelectric element 304.
[0051] The illustrative piezoelectric damping ring 300 includes
sixteen piezoelectric elements 304 coupled to the damping ring 302.
In alternative piezoelectric damping ring embodiments, additional
and/or fewer piezoelectric elements 304 may be coupled to the
damping ring 302. As shown, every other of the piezoelectric
elements 304 is paired (i.e., connected) at an inward facing
surface 316 via a wire 306 to another of the piezoelectric elements
304 at the inward facing surface 316 of that one of the
piezoelectric elements 304. In such an embodiment as the
illustrative embodiment of FIG. 3, the piezoelectric damping ring
300 may support eight engine orders (i.e., N/2, wherein "N"
represents the number of piezoelectric elements 304 and "2"
designates the number of neighboring piezoelectric elements 304
from which the piezoelectric element 304 is wired), or eight nodal
diameters. Accordingly, different engine orders may be supported
based on the number of and the interconnectivity between (see,
e.g., the wiring 306) the piezoelectric elements 304 of the
piezoelectric damping ring 300.
[0052] To do so, one of the connected piezoelectric elements 304
may be excited by the electricity from another of the piezoelectric
elements 304 that it has been connected to via the wiring 306. For
example, as a result of micro-slip, mechanical energy at one of the
piezoelectric elements 304 at one engine order can be converted to
electrical energy and transmitted to another of the piezoelectric
elements 304 at a different engine order via mechanical friction
and dissipated through heat. In use, the electrical energy can be
transferred from an active crossing (see, e.g., the active crossing
510 of FIG. 5) to an inactive crossing (e.g., a crossing at a
different engine order).
[0053] It should be appreciated that additional and/or alternative
wiring methods may be used to support additional engine orders. For
example, in alternative embodiments, the wiring 306 may connect to
different ends of the piezoelectric elements 304 (e.g., positively
and negatively charged portions of the piezoelectric elements 304)
and/or the middle of the piezoelectric elements 304 as shown in
FIG. 3. Additionally or alternatively, in some embodiments, the
underlying blisk 112 may be used as a conductive means to transfer
electricity from one piezoelectric element 304 to another
piezoelectric element 304.
[0054] Accordingly, the wiring 306 running between of the
piezoelectric elements 304 at different locations can facilitate
the flow of electricity from one of the piezoelectric elements 304
to dissipate the energy through mechanical damping at another one
of the piezoelectric elements 304 that is out of phase with the
other of the piezoelectric elements 304. In other words,
[0055] mechanical energy may be extracted from a first
piezoelectric element 304 at a first nodal diameter pattern, which
can be used to excite the piezoelectric damping ring 300 into a
second nodal diameter pattern. Accordingly, the second nodal
diameter pattern of the ring may then dissipate energy through
friction (i.e., generating heat). For example, if one of the
piezoelectric elements 304 at a first position creates motion out
of phase with the motion of a connected other of the piezoelectric
elements 304 at a second position, transferring electricity
converted from the mechanical energy can be used to cancel out
vibration (e.g., via mechanical friction dissipated as heat).
[0056] It should be appreciated that, in some embodiments, more
than one piezoelectric damping ring 300 may be included, either in
the same groove 206 adjacent to another piezoelectric damping ring
300 or be located in another groove such that each of the
piezoelectric damping rings 300 are axisymmetric around the central
axis 114 (i.e., the engine centerline). For example, as shown in
FIG. 4, the groove 206 of FIGS. 2 and 3 is positioned upstream of
another groove 402, which is positioned downstream of the groove
206 at a position that is axisymmetric about the central axis
114.
[0057] It should be appreciated that, in some embodiments, one or
more of the piezoelectric elements 304 may be connected across
resistive elements to generate heat, or power a device, for
example. In other words, one or more of the piezoelectric elements
304 can double as damping elements whose additional energy can be
used to power other devices of the gas turbine engine 100.
[0058] Referring now to FIG. 5, an illustrative Campbell diagram
500 shows example behavior a fan measured in the environment of an
engine (e.g., of the fan 110 of the gas turbine engine 100 of FIG.
1) during different operating modes. The Campbell diagram 500
includes a frequency in Hertz axis along a y-axis 502, a speed in
revolutions per minute (RPM) along an x-axis 504, and a number of
engine order (EO) lines 506. The Campbell diagram 500 additionally
includes output of various modes 508 of the gas turbine engine 100
at increasing operational frequencies and speeds.
[0059] As shown, Mode 4 and the seventh engine (i.e., 7EO) order
crossing could energize a damping ring in the seventh nodal
diameter. In such an embodiment, the piezoelectric elements 304 of
the piezoelectric damping ring 300 may be wired to transmit the
seventh engine order energy to another engine order that does not
have any crossings in the running range of the engine. Accordingly,
the seventh order energy can be converted to electricity and
transmitted to another piezoelectric element 304 at a different
nodal diameter, such that the electricity may be used to dampen
vibration by inducing micro-slip between the piezoelectric damping
ring 300 and the disk 202. In other words, the piezoelectric
damping ring 300 can be excited by the resulting electricity into
another nodal diameter with a crossing outside the running speed of
the engine (e.g., the gas turbine engine 100) where micro-slip
between the blisk and the piezoelectric damping ring would
dissipate the energy (i.e., between the damping ring 302 of the
piezoelectric damping ring 300 and the surface 210 of the disk
202).
[0060] A second blisk assembly 2000 in accordance with the present
disclosure is shown in FIGS. 6 and 7. The blisk assembly 2000
includes a blisk 2112 and a piezoelectric damping ring 2300. The
blisk 2112 is an integrally bladed disk or rotor similar to blisk
112 described above. The piezoelectric damping ring 2300 is coupled
to the blisk 2112 and dampens vibration of the blisk assembly 2000
during use in a gas turbine engine like engine 100.
[0061] The blisk 2112 illustratively includes a disk 2202, a
plurality of blades 2204, and a platform 2205 that are integrated
with one another as shown in FIG. 6. The disk 2202 supports the
blades 2204 and the platform 2205 during rotation of the blisk
2112. The blades 2204 interact with gasses passing through an
engine to compress the gasses. The platform 2205 extends forward
and aft of the blades 2204 to separate the disk 2202 from the
plurality of blades 2204 so that gasses passing over the blades
2204 does not interact with the disk 2202.
[0062] The disk 2202 illustratively includes a drive arm 2220, a
cone shaft 2222, a support ring 2224, and a damper flange 2225 as
shown in FIG. 6. The drive arm 2220 is configured to be coupled to
a shaft to receive rotation from other parts of an engine. The cone
shaft 2222 extends outwardly from the drive arm 2220 to the support
ring 2224. The support ring 2224 supports the blades 2204 and the
platform 2205. The damper flange 2225 is cantilevered and provides
a location for coupling of the piezoelectric damping ring 2300.
[0063] The piezoelectric damping ring 2300 illustratively includes
a damping ring 2302, piezoelectric elements 2304, and wires 2306 as
shown in FIGS. 6 and 7. The damping ring 2302 is a full hoop
component that extends around a central axis 2114. The
piezoelectric elements 2304 are coupled to the damping ring 2302
and are equidistantly spaced from one another circumferentially
around the axis 2114.
[0064] In the illustrative embodiment, the damping ring 2302 is
fastened to the damper flange 2225 by bolts along an inner portion
of the damper ring 2302 as shown in FIG. 6. The damping ring 2303
contacts the platform 2205 near a mid-span of the blades 2204 along
an outer portion of the damper ring 2302 where the damper ring 2302
is free for micro movements relative to the blisk 2112. In the
illustrative embodiments, the piezoelectric elements 2304 are
coupled to the damping ring 2302 along a middle portion of the
damper ring 2302 between the inner and outer portions.
[0065] The piezoelectric elements 2304 are substantially similar to
elements 304 and pass energy from one to another via wires 2306 as
described herein. As described herein, the piezoelectric elements
2304 can dampen vibration in the blisk assembly 2000.
[0066] A third blisk assembly 3000 in accordance with the present
disclosure is shown in FIG. 8. The blisk assembly 3000 includes a
blisk 3112 and a piezoelectric damping ring 3300. The blisk 3112 is
an integrally bladed disk or rotor similar to blisk 112 described
above. The piezoelectric damping ring 3300 is coupled to the blisk
3112 and dampens vibration of the blisk assembly 3000 during use in
a gas turbine engine like engine 100.
[0067] The blisk 3112 illustratively includes a disk 3202, a
plurality of blades 3204, and a platform 3205 that are integrated
with one another as shown in FIG. 8. The disk 3202 supports the
blades 3204 and the platform 3205 during rotation of the blisk
3112. The blades 3204 interact with gasses passing through an
engine to compress the gasses. The platform 3205 extends forward
and aft of the blades 3204 to separate the disk 3202 from the
plurality of blades 3204 so that gasses passing over the blades
3204 does not interact with the disk 3202.
[0068] The disk 3202 illustratively includes a drive arm 3220, a
cone shaft 3222, a support ring 3224, and a damper flange 3225 as
shown in FIG. 8. The drive arm 3220 is configured to be coupled to
a shaft to receive rotation from other parts of an engine. The cone
shaft 3222 extends outwardly from the drive arm 3220 to the support
ring 3224. The support ring 3224 supports the blades 3204 and the
platform 3205. The damper flange 3225 interconnects the cone shaft
3222 and the SUPPORT RING 3224. The damper flange 3225 also
provides a location for coupling of the piezoelectric damping ring
3300.
[0069] The piezoelectric damping ring 3300 illustratively includes
a damping ring 3302, piezoelectric elements 3304, and wires as
shown in FIG. 8. The damping ring 3302 is a full hoop component.
The piezoelectric elements 3304 are coupled to the damping ring
3302 and are equidistantly spaced from one another
circumferentially around the axis 3114.
[0070] In the illustrative embodiment, the damping ring 3302 is
fastened to the damper flange 3225 by bolts along an inner portion
of the damper ring 3302 as shown in FIG. 8. The damping ring 3303
contacts the platform 3205 near a mid-span of the blades 3204 along
an outer portion of the damper ring 3302 where the damper ring 3302
is free for micro movements relative to the blisk 3112. In the
illustrative embodiments, the piezoelectric elements 3304 are
coupled to the damping ring 3302 along a middle portion of the
damper ring 3302 between the inner and outer portions.
[0071] The piezoelectric elements 3304 are substantially similar to
elements 304 and pass energy from one to another via wires as
described herein. As described herein, the piezoelectric elements
3304 can dampen vibration in the blisk assembly 3000.
[0072] A fourth blisk assembly 4000 in accordance with the present
disclosure is shown in FIG. 9. The blisk assembly 4000 includes a
blisk 4112 and a piezoelectric damping ring 4300. The blisk 4112 is
an integrally bladed disk or rotor similar to blisk 112 described
above. The piezoelectric damping ring 4300 is coupled to the blisk
4112 and dampens vibration of the blisk assembly 4000 during use in
a gas turbine engine like engine 100.
[0073] The blisk 4112 illustratively includes a disk 4202, a
plurality of blades 4204, and a platform 4205 that are integrated
with one another as shown in FIG. 9. The disk 4202 supports the
blades 4204 and the platform 4205 during rotation of the blisk
4112. The blades 4204 interact with gasses passing through an
engine to compress the gasses. The platform 4205 extends forward
and aft of the blades 4204 to separate the disk 4202 from the
plurality of blades 4204 so that gasses passing over the blades
4204 does not interact with the disk 4202.
[0074] The disk 4202 illustratively includes a drive arm 4220, a
cone shaft 4222, a support ring 4224, and a damper flange 4225 as
shown in FIG. 9. The drive arm 4220 is configured to be coupled to
a shaft to receive rotation from other parts of an engine. The cone
shaft 4222 extends outwardly from the drive arm 4220 to the support
ring 4224. The support ring 4224 supports the blades 4204 and the
platform 4205. The damper flange 4225 is cantilevered from the cone
shaft 4222 and provides a location for coupling of the
piezoelectric damping ring 4300.
[0075] The piezoelectric damping ring 4300 illustratively includes
a damping ring 4302, piezoelectric elements 4304, and wires as
shown in FIG. 9. The damping ring 4302 is a full hoop component.
The piezoelectric elements 4304 are coupled to the damping ring
4302 and are equidistantly spaced from one another
circumferentially around the axis 4114.
[0076] In the illustrative embodiment, the damping ring 4302 is
fastened to the damper flange 4225 by bolts along an inner portion
of the damper ring 4302 as shown in FIG. 9. The damping ring 4303
contacts the platform 4205 at an aft end of the platform 4205 along
an outer portion of the damper ring 4302 where the damper ring 4302
is free for micro movements relative to the blisk 4112. In the
illustrative embodiments, the piezoelectric elements 4304 are
coupled to the damping ring 4302 along a middle portion of the
damper ring 4302 between the inner and outer portions.
[0077] The piezoelectric elements 4304 are substantially similar to
elements 304 and pass energy from one to another via wires as
described herein. As described herein, the piezoelectric elements
4304 can dampen vibration in the blisk assembly 4000.
[0078] A fifth blisk assembly 5000 in accordance with the present
disclosure is shown in FIG. 10. The blisk assembly 5000 includes a
blisk 5112 and a piezoelectric damping ring 5300. The blisk 5112 is
an integrally bladed disk or rotor similar to blisk 112 described
above. The piezoelectric damping ring 5300 is coupled to the blisk
5112 and dampens vibration of the blisk assembly 5000 during use in
a gas turbine engine like engine 100.
[0079] The blisk 5112 illustratively includes a disk 5202, a
plurality of blades 5204, and a platform 5205 that are integrated
with one another as shown in FIG. 10. The disk 5202 supports the
blades 5204 and the platform 5205 during rotation of the blisk
5112. The blades 5204 interact with gasses passing through an
engine to compress the gasses. The platform 5205 extends forward
and aft of the blades 5204 to separate the disk 5202 from the
plurality of blades 5204 so that gasses passing over the blades
5204 does not interact with the disk 5202.
[0080] The disk 5202 illustratively includes a drive arm 5220, a
cone shaft 5222, a support ring 5224, and a damper flange 5225 as
shown in FIG. 10. The drive arm 5220 is configured to be coupled to
a shaft to receive rotation from other parts of an engine. The cone
shaft 5222 extends outwardly from the drive arm 5220 to the support
ring 5224. The support ring 5224 supports the blades 5204 and the
platform 5205. The damper flange 5225 is cantilevered from the
support ring 5224 and has an L-shaped cross-sectional shape that
extends in a forward direction. The damper flange 5225 provides a
location for coupling of the piezoelectric damping ring 5300.
[0081] The piezoelectric damping ring 5300 illustratively includes
a damping ring 5302, piezoelectric elements 5304, and wires as
shown in FIG. 10. The damping ring 5302 is a full hoop component.
The piezoelectric elements 5304 are coupled to the damping ring
5302 and are equidistantly spaced from one another
circumferentially around the axis 5114.
[0082] In the illustrative embodiment, the damping ring 5302 is
fastened to the damper flange 5225 by bolts along an inner portion
of the damper ring 5302 as shown in FIG. 10. The damping ring 5303
contacts the platform 5205 at a forward end of the platform 5205
along an outer portion of the damper ring 5302 where the damper
ring 5302 is free for micro movements relative to the blisk 5112.
In the illustrative embodiments, the piezoelectric elements 5304
are coupled to the damping ring 5302 along a middle portion of the
damper ring 5302 between the inner and outer portions.
[0083] The piezoelectric elements 5304 are substantially similar to
elements 304 and pass energy from one to another via wires as
described herein. As described herein, the piezoelectric elements
5304 can dampen vibration in the blisk assembly 5000.
[0084] A sixth blisk assembly 6000 in accordance with the present
disclosure is shown in FIG. 11. The blisk assembly 6000 includes a
blisk 6112 and a piezoelectric damping ring 6300. The blisk 6112 is
an integrally bladed disk or rotor similar to blisk 112 described
above. The piezoelectric damping ring 6300 is coupled to the blisk
6112 and dampens vibration of the blisk assembly 6000 during use in
a gas turbine engine like engine 100.
[0085] The blisk 6112 illustratively includes a disk 6202, a
plurality of blades 6204, and a platform 6205 that are integrated
with one another as shown in FIG. 11. The disk 6202 supports the
blades 6204 and the platform 6205 during rotation of the blisk
6112. The blades 6204 interact with gasses passing through an
engine to compress the gasses. The platform 6205 extends forward
and aft of the blades 6204 to separate the disk 6202 from the
plurality of blades 6204 so that gasses passing over the blades
6204 does not interact with the disk 6202.
[0086] The disk 6202 illustratively includes a drive arm 6220, a
cone shaft 6222, and a support ring 6224 as shown in FIG. 11. The
drive arm 6220 is configured to be coupled to a shaft to receive
rotation from other parts of an engine. The cone shaft 6222 extends
outwardly from the drive arm 6220 to the support ring 6224. The
support ring 6224 supports the blades 6204 and the platform
6205.
[0087] The piezoelectric damping ring 6300 illustratively includes
a damping ring 6302, piezoelectric elements 6304, and wires as
shown in FIG. 11. The damping ring 6302 is a full hoop component.
The piezoelectric elements 6304 are coupled to the damping ring
6302 and are equidistantly spaced from one another
circumferentially around the axis 6114.
[0088] In the illustrative embodiment, the damping ring 6302 is
fastened to the drive arm 6220 by bolts along an inner portion of
the damper ring 6302 as shown in FIG. 11. The damping ring 6303
contacts the platform 6205 at a forward end of the platform 6205
along an outer portion of the damper ring 6302 where the damper
ring 6302 is free for micro movements relative to the blisk 6112.
In the illustrative embodiments, the piezoelectric elements 6304
are coupled to the damping ring 6302 along a middle portion of the
damper ring 6302 between the inner and outer portions.
[0089] The piezoelectric elements 6304 are substantially similar to
elements 304 and pass energy from one to another via wires as
described herein. As described herein, the piezoelectric elements
6304 can dampen vibration in the blisk assembly 6000.
[0090] While the disclosure has been illustrated and described in
detail in the foregoing drawings and description, the same is to be
considered as exemplary and not restrictive in character, it being
understood that only illustrative embodiments thereof have been
shown and described and that all changes and modifications that
come within the spirit of the disclosure are desired to be
protected.
* * * * *